[Federal Register Volume 75, Number 71 (Wednesday, April 14, 2010)]
[Rules and Regulations]
[Pages 19209-19212]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-7918]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0056; Directorate Identifier 2009-CE-051-AD;
Amendment 39-16259; AD 2010-08-04]
RIN 2120-AA64
Airworthiness Directives; British Aerospace Regional Aircraft
Model HP.137 Jetstream Mk.1, Jetstream Series 200, Jetstream Series
3101, and Jetstream Model 3201 Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding an existing airworthiness directive (AD)
for the products listed above. This AD results from mandatory
continuing airworthiness information (MCAI) issued by an aviation
authority of another country to identify and correct an unsafe
condition on an aviation product. The MCAI describes the unsafe
condition as:
Cracks have been found in the NLG steering jack piston rod
adjacent to the eye-end. This was caused by excessive torque which
had been applied to the eye-end during assembly of the unit. Severe
cracking, if not detected and corrected, can cause the jack to fail
during operation, which may lead to loss of directional control of
the aeroplane during critical phases of take-off and landing.
[[Page 19210]]
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective May 19, 2010.
On May 19, 2010, the Director of the Federal Register approved the
incorporation by reference of British Aerospace Jetstream Series 3100 &
3200 Service Bulletin No. 32-JA030644, Revision No. 1, dated August 19,
2008; British Aerospace Jetstream Series 3100 & 3200 Service Bulletin
No. 32-JM5414, dated August 6, 2004; and APPH Ltd. Bulletin 32-77,
dated October 2003, listed in this AD.
As of June 26, 2007 (72 FR 28587, May 22, 2007), the Director of
the Federal Register approved the incorporation by reference of BAE
Systems British Aerospace Jetstream Series 3100 & 3200 Service Bulletin
32-JA030644, dated October 6, 2003; and APPH Ltd. Service Bulletin 32-
76, Revision 1, dated August 2003, listed in this AD.
As of May 22, 2003 (68 FR 16195, April 3, 2003), the Director of
the Federal Register approved the incorporation by reference of British
Aerospace Jetstream Series 3100 & 3200 Service Bulletin No. 32-
JA020741, dated November 2, 2002.
ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the Docket Management Facility,
U.S. Department of Transportation, Docket Operations, M-30, West
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Taylor Martin, Aerospace Engineer,
FAA, Small Airplane Directorate, 901 Locust, Room 301, ACE-112, Kansas
City, Missouri 64106; telephone: (816) 329-4138; fax: (816) 329-4090.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to include an AD that would apply to the specified products.
That NPRM was published in the Federal Register on January 21, 2010 (75
FR 3418), and proposed to supersede AD 2007-10-14, Amendment 39-15055
(72 FR 28587, May 22, 2007). That NPRM proposed to correct an unsafe
condition for the specified products. The MCAI states that:
Cracks have been found in the NLG steering jack piston rod
adjacent to the eye-end. This was caused by excessive torque which
had been applied to the eye-end during assembly of the unit. Severe
cracking, if not detected and corrected, can cause the jack to fail
during operation, which may lead to loss of directional control of
the aeroplane during critical phases of take-off and landing.
To address this unsafe condition, the UK CAA issued AD 003-11-
2002 (which references BAE Systems Service Bulletin (SB) 32-
JA020741), requiring an inspection for cracks and a measurement of
the release torque of the piston rod end fitting to determine a new
safe life (remaining fatigue life) for individual units. The revised
safe life was calculated in accordance with the formula provided in
associated APPH Ltd (the NLG Jack manufacturer) SB 32-76.
Following the completion of testing, APPH determined that the
remaining fatigue life needed further reduction and published
inspection criteria and a revised formula for calculating the piston
safe life. This calculation and a revised end fitting tightening
torque are contained in APPH SB 32-76 Revision 1. As a result,
pistons which were previously calculated to have significant
remaining life could possibly be unserviceable.
In response to this development, BAE Systems issued SB 32-
JA030644 so that a revised calculation could be performed to
establish the safe life of NLG steering jack pistons. Where not
previously accomplished, the SB also recognised the need to inspect
the piston for cracking and to measure the torque loading of the
piston to eye-end joint so that safe life calculation could be
performed. This SB superseded the earlier SB 32-JA020741 that
produced an overly optimistic assessment of the component's safe
life. The CAA UK issued AD G-2004-0029, superseding AD 003-11-2002,
to require the accomplishment of these corrective actions.
Subsequent to the original issue of BAE Systems SB 32-JA030644,
APPH introduced a modified unit (optionally installed on aeroplanes
by application of BAE Systems SB 32-JM5414) that incorporates a
strengthened piston with a defined safe life. This safe life is not
calculated in accordance with the instructions of BAE Systems SB 32-
JA030644, but is already declared in BAE Systems SB 32-JA981042,
currently at revision 7. In response to requests for clarification,
BAE Systems has revised SB 32-JA030644 to exclude those aeroplanes
from the `Effectivity' that have the modified steering jack assembly
installed in accordance with BAE modification JM5414.
For the reasons described above, this new AD retains the
requirements of UK CAA AD G-2004-0029, which is superseded, and
confirms that for aeroplanes incorporating BAE modification JM5414,
no further action is required.
Comments
We gave the public the opportunity to participate in developing
this AD. We received no comments on the NPRM or on the determination of
the cost to the public.
Conclusion
We reviewed the available data and determined that air safety and
the public interest require adopting the AD as proposed.
Differences Between This AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the AD.
Costs of Compliance
We estimate that this AD will affect 190 products of U.S. registry.
We also estimate that it will take about 2 work-hours per product to
comply with the basic requirements of this AD. The average labor rate
is $85 per work-hour.
Based on these figures, we estimate the cost of this AD to the U.S.
operators to be $32,300, or $170 per product.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
[[Page 19211]]
For the reasons discussed above, I certify this AD:
(1) Is not a ``significant regulatory action'' under Executive
Order 12866;
(2) Is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and
(3) Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD Docket.
Examining the AD Docket
You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Management Facility
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains the NPRM, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Office (telephone (800) 647-5527) is in the ADDRESSES
section. Comments will be available in the AD docket shortly after
receipt.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-15055 (72 FR
28587; May 22, 2007), and adding the following new AD:
2010-08-04 British Aerospace Regional Aircraft:Amendment 39-16259;
Docket No. FAA-2010-0056; Directorate Identifier 2009-CE-051-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective May 19,
2010.
Affected ADs
(b) This AD supersedes AD 2007-10-14, Amendment 39-15055.
Applicability
(c) This AD applies to Model HP.137 Jetstream Mk.1, Jetstream
Series 200, Jetstream Series 3101, and Jetstream Model 3201
airplanes, all serial numbers, that are:
(1) Equipped with steering jack part number (P/N) 6182-2, P/N
6182-3, or P/N 6182-4; and
(2) Certificated in any category.
Subject
(d) Air Transport Association of America (ATA) Code 32: Landing
Gear.
Reason
(e) The mandatory continuing airworthiness information (MCAI)
states:
Cracks have been found in the NLG steering jack piston rod
adjacent to the eye-end. This was caused by excessive torque which
had been applied to the eye-end during assembly of the unit. Severe
cracking, if not detected and corrected, can cause the jack to fail
during operation, which may lead to loss of directional control of
the aeroplane during critical phases of take-off and landing.
To address this unsafe condition, the UK CAA issued AD 003-11-
2002 (which references BAE Systems Service Bulletin (SB) 32-
JA020741), requiring an inspection for cracks and a measurement of
the release torque of the piston rod end fitting to determine a new
safe life (remaining fatigue life) for individual units. The revised
safe life was calculated in accordance with the formula provided in
associated APPH Ltd (the NLG Jack manufacturer) SB 32-76.
Following the completion of testing, APPH determined that the
remaining fatigue life needed further reduction and published
inspection criteria and a revised formula for calculating the piston
safe life. This calculation and a revised end fitting tightening
torque are contained in APPH SB 32-76 Revision 1. As a result,
pistons which were previously calculated to have significant
remaining life could possibly be unserviceable.
In response to this development, BAE Systems issued SB 32-
JA030644 so that a revised calculation could be performed to
establish the safe life of NLG steering jack pistons. Where not
previously accomplished, the SB also recognised the need to inspect
the piston for cracking and to measure the torque loading of the
piston to eye-end joint so that safe life calculation could be
performed. This SB superseded the earlier SB 32-JA020741 that
produced an overly optimistic assessment of the component's safe
life. The CAA UK issued AD G-2004-0029, superseding AD 003-11-2002,
to require the accomplishment of these corrective actions.
Subsequent to the original issue of BAE Systems SB 32-JA030644,
APPH introduced a modified unit (optionally installed on aeroplanes
by application of BAE Systems SB 32-JM5414) that incorporates a
strengthened piston with a defined safe life. This safe life is not
calculated in accordance with the instructions of BAE Systems SB 32-
JA030644, but is already declared in BAE Systems SB 32-JA981042,
currently at revision 7. In response to requests for clarification,
BAE Systems has revised SB 32-JA030644 to exclude those aeroplanes
from the `Effectivity' that have the modified steering jack assembly
installed in accordance with BAE modification JM5414.
For the reasons described above, this new AD retains the
requirements of UK CAA AD G-2004-0029, which is superseded, and
confirms that for aeroplanes incorporating BAE modification JM5414,
no further action is required.
Actions and Compliance
(f) Unless already done, do the following actions:
(1) For airplanes where the actions in British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin No. 32-JA020741, dated
November 2, 2002 (APPH Ltd. Service Bulletin 32-76, Revision 1,
dated August 2003), have not already been done:
(i) Within 2 months after June 26, 2007 (the effective date
retained from AD 2007-10-14), inspect the steering jack piston rod,
check the torque of the end fitting, and determine the safe life of
the steering jack piston rod following BAE Systems British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin 32-JA030644, dated
October 6, 2003. You may do the actions required in this paragraph
following paragraph 2, Part 1 of British Aerospace Jetstream Series
3100 & 3200 Service Bulletin No. 32-JA030644, Revision No. 1, dated
August 19, 2008, to comply with this AD.
(ii) If the piston rod is found cracked or unserviceable during
the inspection required in paragraph (f)(1)(i) of this AD, before
further flight, remove the steering jack and replace it with a
serviceable unit.
(2) For airplanes where the actions in BAE British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin No. 32-JA020741, dated
November 2, 2002 (APPH Ltd. Service Bulletin 32-76, Revision 1,
dated August 2003), have already been done:
(i) Within 3 months after June 26, 2007 (the effective date
retained from AD 2007-10-14), recalculate the safe life of the
steering jack piston rod and re-torque the piston rod eye-end
following BAE Systems British Aerospace Jetstream Series 3100 & 3200
Service Bulletin 32-JA030644, dated October 6, 2003. You may do the
actions required in this paragraph following paragraph 2, Part 2 of
British Aerospace Jetstream Series 3100 & 3200 Service Bulletin No.
32-JA030644, Revision No. 1, dated August 19, 2008, to comply with
this AD.
(ii) If the piston rod is found unserviceable during the
inspection required in paragraph (f)(2)(i) of this AD, before
further flight, remove the steering jack and replace it with a
serviceable unit.
(3) For airplanes equipped with steering jack part number (P/N)
6182-2, P/N 6182-3, or P/N 6182-4 incorporating Strike-off 4,
installed by BAE Systems modification JM5414 (refer to British
Aerospace Jetstream Series 3100 & 3200 Service Bulletin No. 32-
JM5414, dated August 6, 2004; and APPH Ltd. Bulletin 32-77, dated
October 2003): the actions specified in paragraph (f)(1), (f)(1)(i),
(f)(1)(ii), (f)(2), (f)(2)(i), or (f)(2)(ii) of this AD are not
required.
(4) For all airplanes: After June 26, 2007 (the effective date
retained from AD 2007-10-14), do not install a steering jack piston
rod with P/N 6182-2, P/N 6182-3, or P/N 6182-4, unless it has been
inspected and the safe life recalculated following BAE Systems
[[Page 19212]]
British Aerospace Jetstream Series 3100 & 3200 Service Bulletin 32-
JA030644, dated October 6, 2003. You may inspect and recalculate the
safe life of the steering jack piston rod following paragraph 2 of
British Aerospace Jetstream Series 3100 & 3200 Service Bulletin No.
32-JA030644, Revision No. 1, dated August 19, 2008, to comply with
this AD.
FAA AD Differences
Note: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(g) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
Standards Office, FAA, has the authority to approve AMOCs for this
AD, if requested using the procedures found in 14 CFR 39.19. Send
information to ATTN: Taylor Martin, Aerospace Engineer, FAA, Small
Airplane Directorate, 901 Locust, Room 301, Kansas City, Missouri
64106; telephone: (816) 329-4138; fax: (816) 329-4090. Before using
any approved AMOC on any airplane to which the AMOC applies, notify
your appropriate principal inspector (PI) in the FAA Flight
Standards District Office (FSDO), or lacking a PI, your local FSDO.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(h) Refer to MCAI European Aviation Safety Agency (EASA) AD No.:
2009-0135, dated June 23, 2009; British Aerospace Jetstream Series
3100 & 3200 Service Bulletin No. 32-JA020741, dated November 2,
2002; BAE Systems British Aerospace Jetstream Series 3100 & 3200
Service Bulletin 32-JA030644, dated October 6, 2003; British
Aerospace Jetstream Series 3100 & 3200 Service Bulletin No. 32-
JA030644, Revision No. 1, dated August 19, 2008; British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin No. 32-JM5414, dated
August 6, 2004; APPH Ltd. Service Bulletin 32-76, Revision 1, dated
August 2003; and APPH Ltd. Service Bulletin 32-77, dated October
2003, for related information.
Material Incorporated by Reference
(i) You must use British Aerospace Jetstream Series 3100 & 3200
Service Bulletin No. 32-JA020741, dated November 2, 2002; BAE
Systems British Aerospace Jetstream Series 3100 & 3200 Service
Bulletin 32-JA030644, dated October 6, 2003; British Aerospace
Jetstream Series 3100 & 3200 Service Bulletin No. 32-JA030644,
Revision No. 1, dated August 19, 2008; British Aerospace Jetstream
Series 3100 & 3200 Service Bulletin No. 32-JM5414, dated August 6,
2004; APPH Ltd. Service Bulletin 32-76, Revision 1, dated August
2003; and APPH Ltd. Service Bulletin 32-77, dated October 2003, to
do the actions required by this AD, unless the AD specifies
otherwise.
(1) The Director of the Federal Register approved the
incorporation by reference of British Aerospace Jetstream Series
3100 & 3200 Service Bulletin No. 32-JA030644, Revision No. 1, dated
August 19, 2008; British Aerospace Jetstream Series 3100 & 3200
Service Bulletin No. 32-JM5414, dated August 6, 2004; and APPH Ltd.
Bulletin 32-77, dated October 2003, under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) On June 26, 2007 (72 FR 28587, May 22, 2007), the Director
of the Federal Register previously approved the incorporation by
reference of BAE Systems British Aerospace Jetstream Series 3100 &
3200 Service Bulletin 32-JA030644, dated October 6, 2003; and APPH
Ltd. Service Bulletin 32-76, Revision 1, dated August 2003.
(3) On May 22, 2003 (68 FR 16195, April 3, 2003), the Director
of the Federal Register previously approved the incorporation by
reference of British Aerospace Jetstream Series 3100 & 3200 Service
Bulletin No. 32-JA020741, dated November 2, 2002.
(4) For service information identified in this AD, contact BAE
Systems (Operations) Ltd, Customer Information Department, Prestwick
International Airport, Ayrshire, KA9 2RW, Scotland, United Kingdom;
Telephone +44 1292 675207, Facsimile +44 1292 675704; E-mail:
[email protected].
(5) You may review copies of the service information
incorporated by reference for this AD at the FAA, Central Region,
Office of the Regional Counsel, 901 Locust, Kansas City, Missouri
64106. For information on the availability of this material at the
Central Region, call (816) 329-3768.
(6) You may also review copies of the service information
incorporated by reference for this AD at the National Archives and
Records Administration (NARA). For information on the availability
of this material at NARA, call (202) 741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Kansas City, Missouri, on March 31, 2010.
Steven R. Thompson,
Acting Manager, Small Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-7918 Filed 4-13-10; 8:45 am]
BILLING CODE 4910-13-P